EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E836 HYDROFOIL AIRFOIL (e836-il) Reynolds number: 1,000,000 Max Cl/Cd: 59.07 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e836-il-1000000-n5.txt Download as CSV file: xf-e836-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E836 HYDROFOIL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7639 0.14236 0.14072 0.0025 1.0000 0.0018
-16.250 -0.7701 0.10583 0.10404 -0.0130 1.0000 0.0017
-16.000 -0.8044 0.09404 0.09209 -0.0193 1.0000 0.0017
-15.750 -0.8389 0.08197 0.07986 -0.0255 1.0000 0.0017
-15.500 -0.8536 0.07429 0.07208 -0.0293 1.0000 0.0016
-15.250 -0.8767 0.06503 0.06266 -0.0337 1.0000 0.0016
-14.750 -0.9882 0.05664 0.05390 -0.0423 1.0000 0.0015
-14.500 -1.0221 0.04926 0.04623 -0.0444 1.0000 0.0015
-14.250 -1.0182 0.04705 0.04397 -0.0448 1.0000 0.0015
-14.000 -1.0203 0.04429 0.04110 -0.0449 1.0000 0.0015
-13.750 -1.0582 0.03798 0.03441 -0.0438 1.0000 0.0016
-13.500 -1.0576 0.03587 0.03218 -0.0430 1.0000 0.0016
-13.250 -1.0681 0.03280 0.02890 -0.0413 1.0000 0.0016
-13.000 -1.0708 0.03057 0.02651 -0.0396 1.0000 0.0017
-12.750 -1.0706 0.02866 0.02446 -0.0378 1.0000 0.0018
-12.500 -1.0649 0.02726 0.02295 -0.0362 1.0000 0.0018
-12.250 -1.0607 0.02573 0.02128 -0.0343 1.0000 0.0018
-12.000 -1.0512 0.02469 0.02016 -0.0328 1.0000 0.0019
-11.750 -1.0388 0.02391 0.01934 -0.0314 1.0000 0.0020
-11.500 -1.0289 0.02292 0.01826 -0.0297 1.0000 0.0021
-11.250 -1.0207 0.02180 0.01702 -0.0275 1.0000 0.0021
-11.000 -1.0096 0.02094 0.01608 -0.0256 1.0000 0.0021
-10.750 -0.9970 0.02024 0.01531 -0.0238 1.0000 0.0023
-10.500 -0.9695 0.01911 0.01404 -0.0253 0.9643 0.0023
-10.250 -0.9409 0.01834 0.01313 -0.0267 0.9320 0.0025
-10.000 -0.9291 0.01769 0.01230 -0.0242 0.9055 0.0025
-9.750 -0.9176 0.01709 0.01156 -0.0217 0.8892 0.0026
-9.500 -0.9019 0.01671 0.01109 -0.0198 0.8779 0.0028
-9.250 -0.8876 0.01609 0.01034 -0.0178 0.8685 0.0028
-9.000 -0.8694 0.01562 0.00979 -0.0164 0.8605 0.0029
-8.750 -0.8512 0.01508 0.00915 -0.0150 0.8535 0.0030
-8.500 -0.8319 0.01461 0.00859 -0.0138 0.8470 0.0031
-8.250 -0.8110 0.01422 0.00812 -0.0129 0.8415 0.0032
-8.000 -0.7918 0.01366 0.00745 -0.0116 0.8357 0.0033
-7.750 -0.7723 0.01311 0.00681 -0.0104 0.8306 0.0040
-7.500 -0.7507 0.01269 0.00634 -0.0095 0.8259 0.0046
-7.250 -0.7281 0.01234 0.00597 -0.0088 0.8212 0.0052
-7.000 -0.7052 0.01203 0.00559 -0.0081 0.8169 0.0057
-6.750 -0.6816 0.01172 0.00525 -0.0076 0.8128 0.0065
-6.500 -0.6584 0.01138 0.00487 -0.0069 0.8085 0.0092
-6.250 -0.6342 0.01113 0.00459 -0.0065 0.8046 0.0114
-6.000 -0.6093 0.01091 0.00433 -0.0062 0.8010 0.0126
-5.750 -0.5850 0.01062 0.00405 -0.0057 0.7972 0.0160
-5.500 -0.5602 0.01039 0.00379 -0.0054 0.7933 0.0197
-5.250 -0.5358 0.01012 0.00354 -0.0049 0.7898 0.0273
-5.000 -0.5114 0.00982 0.00329 -0.0046 0.7864 0.0414
-4.750 -0.4874 0.00948 0.00302 -0.0041 0.7827 0.0635
-4.500 -0.4646 0.00906 0.00276 -0.0035 0.7790 0.1022
-4.000 -0.4161 0.00841 0.00234 -0.0026 0.7723 0.1673
-3.750 -0.3924 0.00803 0.00213 -0.0022 0.7686 0.2133
-3.500 -0.3683 0.00768 0.00194 -0.0017 0.7650 0.2587
-3.250 -0.3451 0.00727 0.00174 -0.0012 0.7618 0.3184
-2.750 -0.3030 0.00605 0.00128 0.0007 0.7543 0.5151
-2.500 -0.2780 0.00580 0.00118 0.0010 0.7508 0.5642
-2.250 -0.2514 0.00568 0.00112 0.0011 0.7475 0.5913
-2.000 -0.2240 0.00557 0.00106 0.0011 0.7438 0.6132
-1.750 -0.1966 0.00549 0.00103 0.0011 0.7399 0.6335
-1.500 -0.1689 0.00544 0.00099 0.0010 0.7361 0.6488
-1.250 -0.1409 0.00541 0.00097 0.0008 0.7325 0.6593
-1.000 -0.1126 0.00538 0.00095 0.0007 0.7283 0.6698
-0.750 -0.0845 0.00536 0.00094 0.0005 0.7237 0.6803
-0.500 -0.0564 0.00534 0.00093 0.0003 0.7185 0.6897
-0.250 -0.0282 0.00533 0.00092 0.0002 0.7116 0.6974
0.000 0.0000 0.00534 0.00091 0.0000 0.7048 0.7048
0.250 0.0281 0.00533 0.00092 -0.0002 0.6974 0.7117
0.500 0.0564 0.00534 0.00093 -0.0003 0.6898 0.7186
0.750 0.0844 0.00536 0.00094 -0.0005 0.6803 0.7237
1.000 0.1126 0.00538 0.00095 -0.0006 0.6697 0.7283
1.250 0.1408 0.00541 0.00097 -0.0008 0.6593 0.7325
1.500 0.1688 0.00545 0.00099 -0.0010 0.6486 0.7361
1.750 0.1965 0.00549 0.00103 -0.0011 0.6336 0.7399
2.000 0.2239 0.00557 0.00106 -0.0011 0.6134 0.7438
2.250 0.2513 0.00568 0.00112 -0.0011 0.5911 0.7475
2.500 0.2779 0.00580 0.00118 -0.0010 0.5635 0.7508
2.750 0.3030 0.00605 0.00128 -0.0007 0.5152 0.7543
3.000 0.3230 0.00672 0.00151 0.0005 0.4026 0.7582
3.500 0.3683 0.00767 0.00194 0.0018 0.2597 0.7650
3.750 0.3924 0.00801 0.00213 0.0022 0.2150 0.7685
4.000 0.4160 0.00840 0.00234 0.0027 0.1678 0.7723
4.500 0.4644 0.00906 0.00276 0.0035 0.1021 0.7790
4.750 0.4875 0.00945 0.00301 0.0041 0.0659 0.7828
5.000 0.5113 0.00980 0.00329 0.0046 0.0426 0.7865
5.250 0.5356 0.01012 0.00354 0.0050 0.0275 0.7898
5.500 0.5598 0.01039 0.00379 0.0054 0.0192 0.7933
5.750 0.5847 0.01063 0.00404 0.0058 0.0159 0.7972
6.000 0.6090 0.01091 0.00432 0.0062 0.0125 0.8011
6.250 0.6339 0.01113 0.00459 0.0066 0.0114 0.8047
6.500 0.6581 0.01138 0.00487 0.0070 0.0093 0.8087
6.750 0.6812 0.01172 0.00525 0.0077 0.0064 0.8129
7.000 0.7049 0.01202 0.00559 0.0082 0.0058 0.8170
7.250 0.7278 0.01234 0.00596 0.0089 0.0051 0.8212
7.500 0.7502 0.01270 0.00635 0.0096 0.0045 0.8259
7.750 0.7718 0.01312 0.00682 0.0104 0.0039 0.8307
8.000 0.7908 0.01371 0.00752 0.0118 0.0033 0.8358
8.250 0.8114 0.01416 0.00804 0.0128 0.0032 0.8415
8.500 0.8318 0.01459 0.00856 0.0139 0.0031 0.8470
8.750 0.8508 0.01508 0.00915 0.0151 0.0030 0.8534
9.000 0.8697 0.01556 0.00971 0.0164 0.0029 0.8603
9.250 0.8869 0.01611 0.01037 0.0179 0.0028 0.8685
9.500 0.9027 0.01662 0.01099 0.0197 0.0027 0.8776
9.750 0.9161 0.01716 0.01164 0.0220 0.0026 0.8893
10.000 0.9273 0.01779 0.01241 0.0246 0.0026 0.9060
10.250 0.9400 0.01839 0.01318 0.0268 0.0025 0.9326
10.500 0.9676 0.01939 0.01436 0.0255 0.0024 0.9663
10.750 0.9984 0.02011 0.01516 0.0236 0.0022 1.0000
11.000 1.0098 0.02091 0.01604 0.0256 0.0021 1.0000
11.250 1.0189 0.02193 0.01717 0.0278 0.0021 1.0000
11.500 1.0311 0.02271 0.01802 0.0294 0.0020 1.0000
11.750 1.0384 0.02393 0.01936 0.0315 0.0020 1.0000
12.000 1.0501 0.02477 0.02026 0.0329 0.0019 1.0000
12.250 1.0579 0.02596 0.02155 0.0346 0.0019 1.0000
12.500 1.0674 0.02701 0.02266 0.0360 0.0017 1.0000
12.750 1.0695 0.02875 0.02457 0.0380 0.0018 1.0000
13.000 1.0743 0.03026 0.02619 0.0394 0.0018 1.0000
13.250 1.0731 0.03235 0.02841 0.0410 0.0017 1.0000
13.500 1.0695 0.03474 0.03096 0.0425 0.0016 1.0000
13.750 1.0604 0.03778 0.03419 0.0438 0.0016 1.0000
14.000 1.0380 0.04237 0.03906 0.0448 0.0015 1.0000
14.250 1.0065 0.04849 0.04548 0.0446 0.0015 1.0000
14.750 1.0026 0.05469 0.05186 0.0429 0.0015 1.0000
15.000 0.9587 0.06465 0.06213 0.0385 0.0015 1.0000
15.250 0.9369 0.07253 0.07018 0.0339 0.0015 1.0000
15.500 0.9068 0.08327 0.08111 0.0273 0.0015 1.0000
15.750 0.9362 0.08150 0.07926 0.0284 0.0015 1.0000
16.000 0.9203 0.08968 0.08756 0.0235 0.0016 1.0000
16.250 0.8977 0.09966 0.09766 0.0180 0.0016 1.0000
16.500 0.8702 0.11090 0.10901 0.0121 0.0016 1.0000
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